EP2388520B1 - Lance d'un brûleur d'une turbine à gaz - Google Patents

Lance d'un brûleur d'une turbine à gaz Download PDF

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Publication number
EP2388520B1
EP2388520B1 EP10163443.4A EP10163443A EP2388520B1 EP 2388520 B1 EP2388520 B1 EP 2388520B1 EP 10163443 A EP10163443 A EP 10163443A EP 2388520 B1 EP2388520 B1 EP 2388520B1
Authority
EP
European Patent Office
Prior art keywords
lance
duct
nozzles
terminal portion
spacer
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP10163443.4A
Other languages
German (de)
English (en)
Other versions
EP2388520A1 (fr
Inventor
Ulrich Rathmann
Daniel Burri
Thorsten Motzkus
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Ansaldo Energia IP UK Ltd
Original Assignee
General Electric Technology GmbH
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Technology GmbH filed Critical General Electric Technology GmbH
Priority to ES10163443.4T priority Critical patent/ES2611106T3/es
Priority to EP10163443.4A priority patent/EP2388520B1/fr
Priority to US13/107,135 priority patent/US9182117B2/en
Publication of EP2388520A1 publication Critical patent/EP2388520A1/fr
Application granted granted Critical
Publication of EP2388520B1 publication Critical patent/EP2388520B1/fr
Active legal-status Critical Current
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/106—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting at the burner outlet
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F23D14/22—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone with separate air and gas feed ducts, e.g. with ducts running parallel or crossing each other
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D17/00—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel
    • F23D17/002—Burners for combustion conjointly or alternatively of gaseous or liquid or pulverulent fuel gaseous or liquid fuel
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07021—Details of lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07022—Delaying secondary air introduction into the flame by using a shield or gas curtain

Definitions

  • the present invention relates to a lance of a gas turbine burner.
  • the gas turbine burner is the second burner of a sequential combustion gas turbine engine, i.e. a burner into which hot gases generated in a first combustion chamber but still rich in oxygen pass through, such that a fuel that is injected thereinto increases its temperature and spontaneously burns.
  • a sequential combustion gas turbine engine i.e. a burner into which hot gases generated in a first combustion chamber but still rich in oxygen pass through, such that a fuel that is injected thereinto increases its temperature and spontaneously burns.
  • Burners of the kind described usually have a cylindrical body into which a lance projects.
  • the lance is L-shaped and is usually provided with two or also more than two (i.e. three) coaxial ducts having nozzles at their ends.
  • a lance having the features specified in the preamble of claim 1 is known from US 5 487 659 .
  • the nozzles must have substantially coaxial axes; this feature is of great importance, because through the inner duct a fuel (either liquid or gaseous fuel) passes through, to be injected through the nozzles, and through the outer duct air passes through, to be injected together with the fuel (this is the so called shielding air).
  • a fuel either liquid or gaseous fuel
  • the outer duct In order to connect together the inner and the outer duct, typically the outer duct is provided with a flange at its terminal portion that slidingly rests on the inner duct.
  • this flange withstands large forces that urge it; for example these forces are generated by the fuel and air flowing in the inner and outer ducts.
  • the terminal portions of the ducts (where the nozzles are located) withstand high thermal loads, caused for example by the hot gases flowing in the burner. These thermal loads cause deformations, which may be amplified in case different materials, having different thermal expansion coefficients, are used.
  • the technical aim of the present invention is therefore to provide a lance by which the said problems of the known art are eliminated.
  • an aspect of the invention is to provide a lance having at least an inner duct with inner nozzles and an outer duct with outer nozzles, with the inner and outer nozzles that are substantially aligned and have their axes in a prefixed relative position. During operation no or a very limited shifting of the axes of the substantially aligned inner and outer nozzles, from the correct prefixed relative position, occur.
  • a burner being the second burner of a sequential combustion gas turbine comprises a channel 1 typically having a rectangular or trapezoidal shape, into which a lance 2 extends; in addition, upstream of the lance 2 also vortex generators 3 are provided (in figure 1 the arrow G indicates the direction according to which the hot gases circulate through the channel 1).
  • the lance 2 is L-shaped and has a terminal portion extending parallel to the flow direction of the hot gases.
  • the lance 1 comprises an inner duct 10 with inner nozzles 11; through this duct a fuel passes through, for example gaseous or liquid fuel.
  • the lance 1 also has an annular outer duct 12 that encircles the inner duct 10 and is provided with outer nozzles 13; through this duct air passes through, that during operation is injected together with the fuel (i.e. this is the so called shielding air that allows the fuel to penetrate into the hot gases to improve mixing).
  • the inner and the outer nozzles 11, 13 are provided with axes having a predefinite relative position, i.e. they are substantially coaxial or slightly shifted with respect to one another (i.e. a small offset may be provided therebetween), such that during operation, because of the different thermal expansion of the parts, the axes of the nozzles 11 and 13 are substantially coaxial; for sake of clarity in the attached figures the axes of the inner and outer nozzles 11, 13 are shown as overlapping axes and are all identified by the reference 14.
  • the nozzles 11, 13 are arranged to inject fuel and air in a transversal direction within the channel 1 and, in this respect, the axis 14 is at an angle (preferably perpendicular) to the longitudinal axis 1a of the terminal portion of the lance 2 (in the embodiments shown this axis 1a overlaps the longitudinal axis of the channel 1, but may also be apart from it).
  • a spacer 15 is provided that is fixed to both the inner duct 10 and outer duct 12. Since the spacer 15 is fixed to the terminal portions of the inner and outer ducts 12 no relative movement thereof is possible and, thus, no displacement of the axes of the inner and outer nozzles 11, 13 from the correct position is possible.
  • the spacer 15 extends from the outer duct 12 (i.e. it is realised in one piece with it or it is permanently connected to it, for example by welding) and rests in a seat 16 of the inner duct 10; in addition a fixing element 17 blocking the spacer 15 in the seat 16 is also provided.
  • the spacer 15 may extend from the inner duct 10 (i.e. it is realised in one piece with it or it is permanently connected to it, for example by welding) and rest in a seat 16 of the outer duct 12; also in this case a fixing element 17 blocking the spacer 15 in the seat 16 is provided.
  • the spacer 15 is defined by a collar having through holes 18 allowing the air circulating in the outer duct 12 to pass through.
  • the collar 15 also has slits 19 defining a plurality of separate, all equal elements 20 that extend from the outer duct 12 ( figure 3 ) or inner duct 10 ( figure 5 ).
  • the collar 15 is located between the end of the inner duct 10 and the inner nozzles 11 and, correspondingly, between the end of the outer duct 12 and the outer nozzles 13.
  • the seat 16 is defined by a shoulder and the fixing element 17 is defined by a ring, preferably a threaded ring screwed to a corresponding part of the inner or outer duct 10, 12.
  • the first embodiment of lance 1 is shown in figures 2 and 3 .
  • the collar 15 extends from the outer duct 12 and the seat 16 is provided in the inner duct 10.
  • the ring 17 is a threaded ring that is screwed to a corresponding threaded terminal portion of the inner duct 10.
  • the outer duct 12 has a terminal portion closed by a wall 21 being a separate element from the outer duct 12 and connected thereto, for example by welding.
  • the second embodiment of the lance 1 is shown in figures 4 and 5 .
  • the collar 15 extends from the inner duct 10 and the seat 16 housing it is provided in the outer duct 12.
  • the ring 17 extends from the wall 21 closing the outer duct 12; according to the invention, this wall 21 is a separate element from the outer duct 12 and is connected thereto.
  • the ring 17 is a threaded ring that is screwed to a corresponding threaded terminal portion of the outer duct 12; after screwing also a welding, to secure the connection, may be applied.
  • Figure 6 shows a third embodiment of the lance 1.
  • the lance 1 has a first inner duct 10a arranged to carry a first fuel (typically liquid fuel) and a second inner duct 10b (arranged to carry a second fuel, typically gaseous fuel); the ducts 10a and 10b are coaxial with each other.
  • a first fuel typically liquid fuel
  • a second inner duct 10b arranged to carry a second fuel, typically gaseous fuel
  • An outer duct 12 encircles both inner ducts 10a and 10b and is coaxial with them.
  • Each duct 10a, 10b, 12 has nozzles 11a, 11b and 13 having coaxial axes 14.
  • the terminal portion of the inner duct is welded to the same inner duct 10 (the figures show that the inner duct 10 is made in separate pieces joined together, typically welded).
  • the ring 17 is screwed to the threaded end of the inner duct 10, to block the collar 15 and then also the wall 21 is connected (usually welded) to the outer duct 12.
  • the terminal portion of the inner ducts (a block defines the terminal portions of both inner ducts 10a, 10b) is welded to the inner duct 10a first.
  • the closing element 22 and a second welding to connect the terminal portion to the inner duct 10b are thus applied.
  • the terminal portion of the outer element is welded to the outer duct 12 and, after having screwed the ring 17 to block the collar 15, also the wall 21 in welded to the outer duct 12.
  • the lance in the embodiments of the invention proved to be very effective, since the collar 15 between the outer and inner ducts 12, 10 is connected (i.e. fixed) to both the inner and outer duct 10, 12 and is blocked in all directions, preventing possible relative deformations that would shift the axes of the inner and outer nozzles 11, 13 from the correct relative position (typically being a coaxial or substantially coaxial relative position).

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)

Claims (14)

  1. Lance (2) d'un brûleur de turbine à gaz comprenant au moins un conduit interne (10) avec des buses internes (11) et un conduit externe annulaire (12) encerclant le conduit interne (10) et prévu avec des buses externes (13), dans laquelle, entre une partie terminale du conduit interne (10) et une partie terminale du conduit externe (12), on prévoit au moins un dispositif d'espacement (15), ledit dispositif d'espacement étant fixé à la fois au conduit interne (10) et au conduit externe (12), caractérisée en ce que le conduit externe (12) a une partie terminale fermée par une paroi (21) qui est un élément séparé du conduit externe (12) et raccordée à ce dernier.
  2. Lance (2) selon la revendication 1, caractérisée en ce que le dispositif d'espacement (15) s'étend à partir du conduit externe (12) et s'appuie dans un siège (16) du conduit interne (10) ou vice versa, ladite lance (2) comprenant également un élément de fixation (17) bloquant ledit au moins un dispositif d'espacement (15) dans ledit siège (16).
  3. Lance (2) selon la revendication 1, caractérisée en ce que les buses internes et externes (11, 13) sont prévues avec des axes ayant une position relative prédéfinie.
  4. Lance (2) selon la revendication 3, caractérisée en ce que ladite position relative prédéfinie des axes des buses internes et externes (11, 13) comprend des axes sensiblement coaxiaux ou des axes légèrement décalés les uns par rapport aux autres.
  5. Lance (2) selon la revendication 2, caractérisée en ce que le siège (16) est défini par un épaulement.
  6. Lance (2) selon la revendication 2, caractérisée en ce que l'élément de fixation (17) est défini par une bague.
  7. Lance (2) selon la revendication 6, caractérisée en ce que ladite bague (17) est une bague filetée qui est vissée sur une partie terminale filetée correspondante du conduit interne (10).
  8. Lance (2) selon la revendication 6, caractérisée en ce que ladite bague (17) s'étend à partir de ladite paroi (21) fermant le conduit externe (12).
  9. Lance (2) selon la revendication 8, caractérisée en ce que la bague (17) est une bague filetée qui est vissée sur une partie terminale filetée correspondante du conduit externe (12).
  10. Lance (2) selon l'une quelconque des revendications précédentes, caractérisée en ce que ledit dispositif d'espacement (15) est défini par un collier.
  11. Lance (2) selon la revendication 10, caractérisée en ce que ledit collier (15) a des trous traversants (18) permettant à l'air circulant dans le conduit externe (12) de le traverser.
  12. Lance (2) selon la revendication 11, caractérisée en ce que ledit collier (15) a des fentes (19) définissant une pluralité d'éléments séparés (20).
  13. Lance (2) selon la revendication 12, caractérisée en ce que tous les éléments (20) sont identiques.
  14. Lance (2) selon l'une quelconque des revendications précédentes, caractérisée en ce que le dispositif d'espacement (15) est positionné entre l'extrémité du conduit interne (10) et les buses internes (11) et de manière correspondante, entre l'extrémité du conduit externe (12) et les buses externes (13).
EP10163443.4A 2010-05-20 2010-05-20 Lance d'un brûleur d'une turbine à gaz Active EP2388520B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES10163443.4T ES2611106T3 (es) 2010-05-20 2010-05-20 Lanza de un quemador de una turbina de gas
EP10163443.4A EP2388520B1 (fr) 2010-05-20 2010-05-20 Lance d'un brûleur d'une turbine à gaz
US13/107,135 US9182117B2 (en) 2010-05-20 2011-05-13 Lance of a gas turbine burner

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP10163443.4A EP2388520B1 (fr) 2010-05-20 2010-05-20 Lance d'un brûleur d'une turbine à gaz

Publications (2)

Publication Number Publication Date
EP2388520A1 EP2388520A1 (fr) 2011-11-23
EP2388520B1 true EP2388520B1 (fr) 2016-10-26

Family

ID=42985504

Family Applications (1)

Application Number Title Priority Date Filing Date
EP10163443.4A Active EP2388520B1 (fr) 2010-05-20 2010-05-20 Lance d'un brûleur d'une turbine à gaz

Country Status (3)

Country Link
US (1) US9182117B2 (fr)
EP (1) EP2388520B1 (fr)
ES (1) ES2611106T3 (fr)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2789915A1 (fr) * 2013-04-10 2014-10-15 Alstom Technology Ltd Procédé de fonctionnement d'une chambre de combustion et chambre de combustion
US10094570B2 (en) 2014-12-11 2018-10-09 General Electric Company Injector apparatus and reheat combustor
US10094571B2 (en) 2014-12-11 2018-10-09 General Electric Company Injector apparatus with reheat combustor and turbomachine
US10107498B2 (en) 2014-12-11 2018-10-23 General Electric Company Injection systems for fuel and gas
US10094569B2 (en) 2014-12-11 2018-10-09 General Electric Company Injecting apparatus with reheat combustor and turbomachine
EP3657072B1 (fr) * 2018-11-23 2021-08-11 Ansaldo Energia Switzerland AG Lance pour un brûleur et un procédé de modernisation d'une lance

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DE1937795A1 (de) * 1969-07-25 1971-02-04 Siemens Ag Abstandhalter aus schlecht waermeleitendem Material zwischen je zwei einander umschliessenden Rohren,insbesondere bei tiefgekuehlten Kabeln
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IT1263683B (it) * 1992-08-21 1996-08-27 Westinghouse Electric Corp Complesso di ugello per combustibile per una turbina a gas
DE4326802A1 (de) * 1993-08-10 1995-02-16 Abb Management Ag Brennstofflanze für flüssige und/oder gasförmige Brennstoffe sowie Verfahren zu deren Betrieb
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EP2400216B1 (fr) * 2010-06-23 2014-12-24 Alstom Technology Ltd Lance de brûleur post-combustion

Also Published As

Publication number Publication date
EP2388520A1 (fr) 2011-11-23
US20110284669A1 (en) 2011-11-24
US9182117B2 (en) 2015-11-10
ES2611106T3 (es) 2017-05-04

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